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Simulation of three-dimensional shear flow around a nozzle-afterbody at high speeds

Journal Article · · Journal of Fluids Engineering; (United States)
DOI:https://doi.org/10.1115/1.2910013· OSTI ID:6945692
;  [1]
  1. Mechanical Engineering and Mechanics Dept., Old Dominion Univ., Norfolk, VA (United States)

In this paper, turbulent shear flows at supersonic and hypersonic speeds around a nozzle-afterbody are simulated. The three-dimensional, Reynolds-averaged Navier-Stokes equations are solved by a finite-volume and implicit method. The convective and the pressure terms are differenced by an upwind-biased algorithm. The effect of turbulence is incorporated by a modified Baldwin-Lomax eddy viscosity model. The success of the standard Baldwin-Lomax model for this flow type is shown by comparing it to a laminar case. These modifications made to the model are also shown to improve flow prediction when compared to the standard Baldwin-Lomax model. These modifications to the model reflect the effects of high compressibility, multiple walls, vortices near walls, and turbulent memory effects in the shear layer. This numerically simulated complex flowfield includes a supersonic duct flow, a hypersonic flow over an external double corner, a flow through a non-axisymmetric, internal-external nozzle, and a three-dimensional shear layer. The specific application is for the flow around the nozzle-afterbody of a generic hypersonic vehicle powered by a scramjet engine. The computed pressure distributions compared favorably with the experimentally obtained surface and off-surface flow surveys.

OSTI ID:
6945692
Journal Information:
Journal of Fluids Engineering; (United States), Journal Name: Journal of Fluids Engineering; (United States) Vol. 114:2; ISSN 0098-2202; ISSN JFEGA4
Country of Publication:
United States
Language:
English